GOE 681 AIRFOIL (goe681-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 681 AIRFOIL (goe681-il) Reynolds number: 100,000 Max Cl/Cd: 44.27 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe681-il-100000.txt Download as CSV file: xf-goe681-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 681 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2899 0.10408 0.09954 -0.0563 0.9685 0.1707
-8.250 -0.4519 0.06441 0.05930 -0.0764 0.9483 0.0974
-8.000 -0.4505 0.05875 0.05340 -0.0789 0.9398 0.0955
-7.750 -0.4615 0.05402 0.04836 -0.0783 0.9288 0.0945
-7.500 -0.4596 0.04824 0.04201 -0.0797 0.9218 0.0939
-7.250 -0.4636 0.04527 0.03865 -0.0770 0.9111 0.0940
-7.000 -0.4446 0.04172 0.03455 -0.0777 0.9051 0.0945
-6.750 -0.4372 0.03969 0.03211 -0.0755 0.8961 0.0950
-6.500 -0.4162 0.03755 0.02951 -0.0751 0.8894 0.0958
-6.250 -0.3805 0.03544 0.02700 -0.0769 0.8854 0.0974
-6.000 -0.3716 0.03470 0.02625 -0.0741 0.8753 0.0988
-5.750 -0.3389 0.03358 0.02505 -0.0751 0.8698 0.1019
-5.500 -0.2977 0.03229 0.02340 -0.0773 0.8663 0.1069
-5.250 -0.2922 0.03192 0.02317 -0.0739 0.8556 0.1094
-5.000 -0.2573 0.03102 0.02218 -0.0749 0.8503 0.1160
-4.750 -0.2130 0.02988 0.02112 -0.0775 0.8472 0.1255
-4.500 -0.2118 0.02985 0.02107 -0.0732 0.8359 0.1318
-4.250 -0.1765 0.02935 0.02072 -0.0742 0.8305 0.1518
-4.000 -0.1306 0.02907 0.02044 -0.0768 0.8274 0.1855
-3.750 -0.1356 0.02964 0.02110 -0.0715 0.8147 0.1949
-3.500 -0.0956 0.02936 0.02069 -0.0731 0.8100 0.2226
-3.250 -0.0408 0.02865 0.02013 -0.0771 0.8074 0.2498
-3.000 -0.0433 0.02910 0.02047 -0.0719 0.7931 0.2626
-2.750 0.0149 0.02807 0.01961 -0.0760 0.7893 0.2927
-2.500 0.0326 0.02795 0.01947 -0.0740 0.7787 0.3083
-2.250 0.0708 0.02724 0.01872 -0.0750 0.7720 0.3268
-2.000 0.1202 0.02629 0.01770 -0.0778 0.7683 0.3455
-1.750 0.1294 0.02644 0.01796 -0.0746 0.7568 0.3552
-1.500 0.1713 0.02564 0.01716 -0.0761 0.7512 0.3727
-1.250 0.2201 0.02466 0.01620 -0.0787 0.7472 0.3943
-1.000 0.2272 0.02498 0.01651 -0.0751 0.7346 0.4081
-0.750 0.2712 0.02404 0.01568 -0.0769 0.7294 0.4316
-0.500 0.2914 0.02388 0.01561 -0.0752 0.7193 0.4516
-0.250 0.3273 0.02307 0.01499 -0.0757 0.7117 0.4846
0.000 0.3756 0.02169 0.01402 -0.0780 0.7070 0.5665
0.250 0.4990 0.02057 0.01399 -0.0927 0.6941 0.9454
0.500 0.6262 0.01989 0.01294 -0.1101 0.6820 0.9978
0.750 0.6545 0.01960 0.01245 -0.1100 0.6710 1.0000
1.000 0.6672 0.01964 0.01239 -0.1072 0.6583 1.0000
1.250 0.6950 0.01932 0.01185 -0.1066 0.6481 1.0000
1.500 0.7081 0.01935 0.01180 -0.1037 0.6341 1.0000
1.750 0.7244 0.01936 0.01170 -0.1013 0.6204 1.0000
2.000 0.7475 0.01924 0.01139 -0.1000 0.6075 1.0000
2.250 0.7695 0.01915 0.01113 -0.0984 0.5934 1.0000
2.500 0.7841 0.01925 0.01113 -0.0957 0.5773 1.0000
2.750 0.8007 0.01935 0.01111 -0.0933 0.5612 1.0000
3.000 0.8185 0.01946 0.01108 -0.0912 0.5453 1.0000
3.250 0.8372 0.01961 0.01107 -0.0892 0.5298 1.0000
3.500 0.8578 0.01979 0.01105 -0.0875 0.5151 1.0000
3.750 0.8764 0.02005 0.01115 -0.0856 0.5007 1.0000
4.000 0.8913 0.02042 0.01143 -0.0832 0.4865 1.0000
4.250 0.9096 0.02078 0.01167 -0.0813 0.4741 1.0000
4.500 0.9336 0.02109 0.01176 -0.0804 0.4630 1.0000
4.750 0.9467 0.02157 0.01222 -0.0778 0.4514 1.0000
5.000 0.9695 0.02200 0.01248 -0.0768 0.4420 1.0000
5.250 0.9860 0.02249 0.01296 -0.0748 0.4325 1.0000
5.500 1.0111 0.02299 0.01329 -0.0743 0.4249 1.0000
5.750 1.0257 0.02358 0.01391 -0.0720 0.4168 1.0000
6.000 1.0529 0.02406 0.01422 -0.0719 0.4099 1.0000
6.250 1.0675 0.02474 0.01495 -0.0698 0.4031 1.0000
6.500 1.0869 0.02531 0.01549 -0.0684 0.3964 1.0000
6.750 1.1193 0.02591 0.01589 -0.0692 0.3908 1.0000
7.000 1.1283 0.02670 0.01683 -0.0662 0.3854 1.0000
7.250 1.1455 0.02742 0.01759 -0.0646 0.3803 1.0000
7.500 1.1724 0.02807 0.01815 -0.0646 0.3756 1.0000
7.750 1.1978 0.02891 0.01895 -0.0645 0.3714 1.0000
8.000 1.2048 0.02984 0.02006 -0.0613 0.3670 1.0000
8.250 1.2194 0.03068 0.02096 -0.0595 0.3625 1.0000
8.500 1.2437 0.03141 0.02166 -0.0591 0.3585 1.0000
8.750 1.2790 0.03234 0.02246 -0.0607 0.3550 1.0000
9.000 1.2792 0.03354 0.02390 -0.0567 0.3520 1.0000
9.250 1.2830 0.03480 0.02533 -0.0535 0.3488 1.0000
9.500 1.2909 0.03598 0.02662 -0.0509 0.3454 1.0000
9.750 1.3075 0.03695 0.02765 -0.0496 0.3421 1.0000
10.000 1.3359 0.03785 0.02850 -0.0500 0.3390 1.0000
10.250 1.3528 0.03929 0.02999 -0.0490 0.3362 1.0000
10.500 1.3319 0.04126 0.03224 -0.0428 0.3340 1.0000
10.750 1.3022 0.04356 0.03476 -0.0357 0.3319 1.0000
11.000 1.2640 0.04673 0.03815 -0.0290 0.3296 1.0000
12.000 1.3045 0.05376 0.04539 -0.0242 0.3192 1.0000
12.250 0.6415 0.14087 0.13330 -0.0417 0.3581 1.0000
12.500 0.6737 0.14398 0.13643 -0.0417 0.3560 1.0000
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Polar data table (+)
Polar graphs
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